Boron-Epoxy-Reinforced Titanium Aircraft Landing-Gear Drag Strut.

Abstract

The structural performance of a boron-epoxy-reinforced titanium drag strut, containing a bonded scarf joint and designed to the criteria of a large commercial transport, has been evaluated experimentally and analytically. The strut was exposed to two lifetimes of fatigue loading and was statically loaded to the tensile and compressive design ultimate loads. Throughout the test program no evidence of any damage in the drag strut was detected by strain-gage measurements, ultrasonic inspection, or visual observation. The bonded joint was analyzed using the NASTRAN(R) (NASA Structural Analysis) computer program. A comparison of the strains predicted by the NASTRAN computer program with the experimentally determined values shows excellent agreement. An analytical study indicated that the nonlinear behavior of a structural spacer at each end of the strut could be explained by the inelastic behavior and possible creep of the adhesive. (AN)

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Document Details

Document Type
Technical Report
Publication Date
Nov 01, 1976
Accession Number
ADA305550

Entities

People

  • William A. Howell

Organizations

  • Langley Research Center

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Airframes
  • Bonded Joints
  • Commercial Aircraft
  • Composite Materials
  • Computer Programs
  • Fatigue Tests (Mechanics)
  • Honeycomb Cores
  • Landing Gear
  • Materials
  • Mechanical Properties
  • Shear Stresses
  • Strain Gages
  • Stress Strain Relations
  • Stresses
  • Test And Evaluation
  • Transport Aircraft

Fields of Study

  • Materials science
  • Physics

Readers

  • Aerospace Engineering
  • Structural Health Monitoring of Composite Structures.